AH 93-157 (ah93157-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-157 (ah93157-il) Reynolds number: 200,000 Max Cl/Cd: 66.24 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93157-il-200000-n5.txt Download as CSV file: xf-ah93157-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-157
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2177 0.08988 0.08550 -0.1013 0.8461 0.0218
-11.750 -0.2320 0.08310 0.07875 -0.1044 0.8421 0.0217
-11.500 -0.4281 0.04615 0.04128 -0.1230 0.8346 0.0200
-11.250 -0.4447 0.04334 0.03825 -0.1212 0.8303 0.0201
-11.000 -0.4583 0.04097 0.03570 -0.1185 0.8254 0.0203
-10.750 -0.4727 0.03857 0.03305 -0.1149 0.8207 0.0204
-10.500 -0.4815 0.03678 0.03102 -0.1110 0.8169 0.0207
-10.250 -0.4864 0.03498 0.02896 -0.1075 0.8132 0.0210
-10.000 -0.4856 0.03311 0.02682 -0.1045 0.8095 0.0214
-9.750 -0.4808 0.03129 0.02470 -0.1020 0.8062 0.0219
-9.500 -0.4723 0.02953 0.02259 -0.0997 0.8032 0.0226
-9.250 -0.4607 0.02788 0.02051 -0.0977 0.8005 0.0234
-9.000 -0.4446 0.02680 0.01932 -0.0964 0.7976 0.0241
-8.750 -0.4266 0.02607 0.01852 -0.0953 0.7945 0.0248
-8.500 -0.4078 0.02534 0.01768 -0.0943 0.7916 0.0258
-8.250 -0.3878 0.02435 0.01650 -0.0933 0.7889 0.0266
-8.000 -0.3666 0.02334 0.01526 -0.0925 0.7864 0.0277
-7.750 -0.3441 0.02245 0.01414 -0.0917 0.7842 0.0286
-7.500 -0.3231 0.02174 0.01344 -0.0910 0.7815 0.0298
-7.250 -0.3015 0.02126 0.01294 -0.0903 0.7785 0.0314
-7.000 -0.2790 0.02067 0.01225 -0.0896 0.7756 0.0330
-6.750 -0.2557 0.02007 0.01150 -0.0889 0.7729 0.0347
-6.500 -0.2335 0.01941 0.01082 -0.0882 0.7706 0.0362
-6.250 -0.2101 0.01899 0.01036 -0.0877 0.7686 0.0385
-6.000 -0.1871 0.01860 0.00988 -0.0870 0.7660 0.0412
-5.750 -0.1659 0.01812 0.00941 -0.0861 0.7628 0.0438
-5.500 -0.1434 0.01775 0.00903 -0.0853 0.7598 0.0468
-5.250 -0.1198 0.01744 0.00864 -0.0847 0.7572 0.0508
-5.000 -0.0970 0.01703 0.00824 -0.0840 0.7547 0.0555
-4.750 -0.0725 0.01673 0.00786 -0.0836 0.7526 0.0611
-4.500 -0.0500 0.01641 0.00758 -0.0828 0.7500 0.0684
-4.250 -0.0280 0.01617 0.00736 -0.0820 0.7467 0.0770
-4.000 -0.0050 0.01592 0.00713 -0.0813 0.7435 0.0889
-3.750 0.0184 0.01563 0.00690 -0.0807 0.7408 0.1055
-3.500 0.0423 0.01533 0.00666 -0.0801 0.7384 0.1297
-3.250 0.0662 0.01499 0.00642 -0.0796 0.7363 0.1647
-3.000 0.0866 0.01469 0.00633 -0.0786 0.7330 0.2142
-2.750 0.1055 0.01429 0.00625 -0.0773 0.7295 0.2893
-2.500 0.1233 0.01376 0.00611 -0.0759 0.7263 0.3908
-2.000 0.1613 0.01304 0.00687 -0.0707 0.7215 0.7521
-1.750 0.1867 0.01344 0.00724 -0.0694 0.7189 0.8004
-1.500 0.2042 0.01369 0.00747 -0.0673 0.7145 0.8257
-1.250 0.2244 0.01391 0.00761 -0.0656 0.7110 0.8445
-1.000 0.2481 0.01415 0.00776 -0.0644 0.7081 0.8584
-0.750 0.2760 0.01439 0.00793 -0.0637 0.7058 0.8696
-0.500 0.3006 0.01469 0.00819 -0.0624 0.7027 0.8834
-0.250 0.3259 0.01501 0.00850 -0.0612 0.6985 0.8979
0.000 0.3584 0.01516 0.00862 -0.0617 0.6951 0.9091
0.250 0.3806 0.01515 0.00854 -0.0604 0.6920 0.9180
0.500 0.4147 0.01505 0.00835 -0.0618 0.6896 0.9198
0.750 0.4390 0.01507 0.00838 -0.0614 0.6848 0.9223
1.000 0.4633 0.01503 0.00831 -0.0609 0.6804 0.9250
1.250 0.4864 0.01492 0.00815 -0.0602 0.6769 0.9281
1.500 0.5059 0.01479 0.00795 -0.0586 0.6740 0.9316
1.750 0.5285 0.01482 0.00802 -0.0580 0.6683 0.9335
2.000 0.5555 0.01477 0.00795 -0.0580 0.6637 0.9353
2.250 0.5836 0.01465 0.00779 -0.0582 0.6601 0.9369
2.500 0.6046 0.01464 0.00779 -0.0572 0.6550 0.9394
2.750 0.6218 0.01461 0.00777 -0.0554 0.6495 0.9426
3.000 0.6420 0.01450 0.00763 -0.0540 0.6453 0.9450
3.250 0.6682 0.01449 0.00764 -0.0540 0.6399 0.9465
3.500 0.6927 0.01449 0.00766 -0.0536 0.6338 0.9482
3.750 0.7209 0.01440 0.00753 -0.0539 0.6291 0.9494
4.000 0.7397 0.01445 0.00763 -0.0525 0.6223 0.9516
4.250 0.7626 0.01442 0.00761 -0.0518 0.6163 0.9538
4.500 0.7825 0.01440 0.00760 -0.0505 0.6104 0.9562
4.750 0.8000 0.01442 0.00765 -0.0488 0.6031 0.9583
5.000 0.8281 0.01439 0.00762 -0.0491 0.5970 0.9593
5.250 0.8506 0.01449 0.00778 -0.0486 0.5886 0.9612
5.500 0.8771 0.01451 0.00779 -0.0486 0.5814 0.9627
5.750 0.8970 0.01461 0.00794 -0.0475 0.5723 0.9647
6.000 0.9185 0.01467 0.00802 -0.0467 0.5640 0.9665
6.250 0.9381 0.01476 0.00813 -0.0455 0.5551 0.9687
6.500 0.9570 0.01490 0.00830 -0.0442 0.5455 0.9712
6.750 0.9829 0.01505 0.00846 -0.0444 0.5361 0.9728
7.000 1.0040 0.01527 0.00872 -0.0437 0.5251 0.9748
7.250 1.0246 0.01551 0.00900 -0.0430 0.5139 0.9770
7.500 1.0452 0.01578 0.00928 -0.0423 0.5022 0.9793
7.750 1.0652 0.01608 0.00959 -0.0416 0.4901 0.9818
8.000 1.0858 0.01647 0.01001 -0.0412 0.4771 0.9845
8.250 1.1059 0.01691 0.01048 -0.0408 0.4637 0.9885
8.500 1.1220 0.01741 0.01100 -0.0398 0.4495 0.9967
8.750 1.1276 0.01794 0.01152 -0.0368 0.4364 1.0000
9.000 1.1312 0.01850 0.01207 -0.0335 0.4234 1.0000
9.250 1.1379 0.01915 0.01270 -0.0309 0.4102 1.0000
9.500 1.1448 0.01990 0.01343 -0.0285 0.3954 1.0000
9.750 1.1496 0.02083 0.01433 -0.0260 0.3772 1.0000
10.000 1.1520 0.02196 0.01538 -0.0235 0.3559 1.0000
10.250 1.1539 0.02320 0.01653 -0.0210 0.3346 1.0000
10.500 1.1572 0.02448 0.01775 -0.0189 0.3134 1.0000
10.750 1.1611 0.02579 0.01900 -0.0170 0.2946 1.0000
11.000 1.1649 0.02716 0.02032 -0.0152 0.2767 1.0000
11.250 1.1684 0.02862 0.02175 -0.0134 0.2574 1.0000
11.500 1.1708 0.03022 0.02328 -0.0117 0.2369 1.0000
11.750 1.1719 0.03198 0.02497 -0.0100 0.2167 1.0000
12.000 1.1743 0.03373 0.02667 -0.0086 0.1971 1.0000
12.250 1.1736 0.03580 0.02864 -0.0071 0.1742 1.0000
12.500 1.1740 0.03788 0.03064 -0.0058 0.1538 1.0000
12.750 1.1719 0.04024 0.03289 -0.0045 0.1314 1.0000
13.000 1.1709 0.04260 0.03518 -0.0034 0.1110 1.0000
13.500 1.1679 0.04767 0.04010 -0.0016 0.0757 1.0000
13.750 1.1668 0.05030 0.04267 -0.0009 0.0626 1.0000
14.000 1.1667 0.05292 0.04528 -0.0004 0.0527 1.0000
14.250 1.1670 0.05558 0.04795 0.0000 0.0457 1.0000
14.500 1.1673 0.05829 0.05069 0.0003 0.0404 1.0000
14.750 1.1687 0.06098 0.05344 0.0004 0.0363 1.0000
15.000 1.1682 0.06395 0.05647 0.0005 0.0332 1.0000
15.250 1.1689 0.06685 0.05946 0.0004 0.0307 1.0000
15.500 1.1693 0.06985 0.06256 0.0002 0.0283 1.0000
15.750 1.1664 0.07331 0.06607 -0.0001 0.0264 1.0000
16.000 1.1669 0.07645 0.06932 -0.0005 0.0249 1.0000
16.250 1.1665 0.07974 0.07272 -0.0010 0.0237 1.0000
16.500 1.1650 0.08324 0.07631 -0.0017 0.0225 1.0000
16.750 1.1604 0.08722 0.08036 -0.0026 0.0215 1.0000
17.000 1.1595 0.09074 0.08399 -0.0034 0.0206 1.0000
17.250 1.1587 0.09433 0.08771 -0.0044 0.0196 1.0000
17.500 1.1578 0.09796 0.09144 -0.0054 0.0187 1.0000
17.750 1.1559 0.10179 0.09536 -0.0067 0.0180 1.0000
18.000 1.1529 0.10579 0.09944 -0.0080 0.0175 1.0000
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Polar data table (+)
Polar graphs
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